Power conversion machine



4 Sheets-Sheet l Original Filed March 29, 1946 A/AA E NE KEY .NNY

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Aug 5, 1952 F. J. GARDINER 2,605,956

POWER CONVERSION MACHINE Original Filed March 29, 1946 4 Sheelzs-Shee'rI 2 m, 4/ 4g/f A M# ZMWUHUHUHUHWU u u UU /fLH JFUHUHUPUHU Umm 11b/7;(

Aug. 5, 1952 F. J. GARDINER 2,605,956

POWER CONVERSION MACHINE Original Filed March 29, 1946 4 Sheet's-Sheet 5 INVENTOR.

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F. J. GA RDINER POWER CONVERSION MA Aug.. 5, 1952 CHINE Original Filed March 29, 1946 4 Sheets-Sheet 4 Patented Aug. 5, 1952 v I Y UNITED STATES OFFICE BON/VER CONVERSION MACHINE Frank J, Gardiner, Berwyn, Pa., assigner to Chrysler Corporation, Highland Park, Mich., a corporation of Delaware Continuation of Aapplication Serial No. 658,055,

March 29, 1946 rihis application August 1 3, 194.9, Serial No. 110,167 f This application is a continuation of application Serial No. 658,055, filed March 29, 1946, now abandoned, and relates to rotary power conversion machines including axial-now compressors, turbines, pumps, and the like. More speciiically, the invention involves improving the eliiciency of such machines by more efficient and increased energy interchange between the machines and the compressible fluid passing through the machines. For axial-now compressors, larger quantities of energy may be added tothe gas being compressed if appropriate types of flow are maintained in various stages of the compressor. It has been previously kno-Wn that some other flow than vortex flow might be desirable, because energy cannot be added efficiently to a fluid having vortex flow, or inr other words, energy cannot be added in as great a quantity per stage with given Mach number and maximum lift coeicient as when the flow is other than vortex ow. This can be easily demonstrated by the drawing of velocity diagrams, which for vortex flow will not be symmetrical and will consequently indicate that energy cannot be added eiiciently. In spite of this knowledge little progress has been made toward the attainment of improved eilciency through proper iloW, and this may have been due toy the erroneous assumption that a lixed inlet grid or blade stage for an axial compressor would provide solid iiow with uniform axial velocity or -a iiow with uniform axial velocity substantially different from vortex flow.

That a stationary initial stage will produce only vortex ow with constant axial velocity can be demonstrated as follows: Y

The condition of equilibrium in a uid having velocity components in the axial and tangential directions only is expressedv by the following equations;

51 Claims. (CL E30-.122)

By my inventioniI recognize this factY and so take care to transform the vortex flow due to the .fixed inlet to another type4 of' flow to which energy may be efficiently added. I provide for the sumcient addition of energy to the gas being com,- pressed While it has the appropriate type of 110W and then transform the ow to Vortex and finally to axial. For turbines operating on compressible. fluid I arrange for a similar procedure. The iiuid is transformed from axial flow to vortex flow and then to a now from which energy may be efiiciently abstracted. Then the fluid is reconverted to Vortex flow and to axial ow.

By my invention I have provided appropriate stationary and rotary blade stages in turbines and compressors thatwill make definite provision for the appropriate conversion of the flow of the iiuid as outlined above.

'An object of the present invention is. to provide improvements in rotary power conversion machines such as axial-flow compressors and turbines operating on or by compressible fluids, the improvements involving the :appropriateA ar rangement of blade stages required for eiiicient energy transfer With respect to the machines. My machines provide for the'successive transformation of the now of fluids passing therethrough from axial to vortex to a form that may be approximately solid ow, with respect to which the energy transfer is carried out; then back to vortex and axial, in which condition the iluid leaves the machines.

Another object of the invention is to improve a rotary power conversion machine in such a Way as to insure with certainty that the fluid passing through the machine is converted to the proper approximation of solid ilow, in which condition the energy transfer with respect to the fluid is to be made. I have discovered that this approx- 40 imation of solid oW is solid flow minus a Vortex W :.l/aeT/l-tlgg-luv:La fioW and should have a variable axial veloclty. 7 r r T Other objects will appear from the disclosure. where In thedrawings: gfelnergy. Fig. 1 is a diagrammatic partial View in section Va=laxial velocity Vtezta-ngential velocity rzradius With the axial velocity constant, as is the case with straight flow of iiuid into the fixed inlet stage, and with the energy remaining constant with radii, since the uniform energy distribution of straight now' into the ixed inlet stage cannot be changed by the fixed inlet stage, the above equation becomes:

in ne.,

r 'rl This is satised only by Vrrzconstant, Which iS dellition of vortex flow. f

of a compressor of the present invention;

Fig. 2 is a view sho-wing tangential velocity diagrams for various regions ofthe compressor of Fig. 1;

Fig. 3 is a view showing axial velocity diagrams for various regions of the compressor;

'Figc is a View showing4 energy diagrams for various regions of the'compressor;

Fig. 5 is a more detailed physical showingV of a compressor of the present invention;-

Fig. 6 is illustrative of the Velocity diagrams along certain specified sections of the blading of the compressor of Fig. 5;

Fig. 7 shows certain velocity vectors of the diagrams of Fig. 6 in superimposed relation; and

Fig. 8 is illustrative of the velocity diagrams along other specified sections of the blading of the compressor of Fig. 5.

In Fig. 1 is shown a compressor of the axial flow type, designated by the reference character I0. The compressor comprises a stator II and a rotor I2, having an axis ofy rotation beneath the portion of the rotor shown, as viewed in Fig. 1. The stator II has a blade stage I3 forming an inlet for gas or compressible fluid to be compressed by the compressor I0, flowing from left to right therethrough, as viewed in Fig. l. To the right of the stationary blade stage i3 is a rotary blade stage I4 carried by the rotor I2 and a stationary blade stagev I5 carried by the stator Il. The stages I4 and I5 constitute an inducer. To the right of stage I5 are a rotary blade stage I6 carried by the rotor I2 and a stationary blade stage I'I carried by the stator II. The stages I6 and I1 constitute the compressor proper of the axial compressor I0. To the right of the stage Il are a rotary blade stage I8 carried by the rotor I2 and a stationary blade stage I9 carried by the stator II, which'stages constitute an educer. To the right of the stage I9 is a stationary blade stage 20, which constitutes an outlet for the compressed fluidfrom the compressor.

Each of Figs. 2, 3, ande constitutes a set of diagrams representing successive conditions of the iiow of compressible fluid throuh the compressor I0. Each diagram` represents a condition of velocity or energy at exit of the flow from the stage below the right side of which the diagram is positioned and is designated with the reference character of the particular blade stage with a, b, or c added, depending upon whether the diagram is of tangential velocity, axial velocity, or energy. Exceptions are made of the diagrams at the extreme left, which are designated by 10, 10b, and 10 and represent conditions of velocity and energy upon entrance of the compressible iiuid to the flrst stationary stage. Each diagram by its lateral dimension represents a relative quantity of velocity or energy. `The relative quantity of velocity or energy is represented for the various points from stator blade tip to stator blade root and from rotor blade root to rotor blade tip by the lateral dimensions of the diagrams at the corresponding points thereon from bottom to top. y

Consider Diagrams 10a, 10b, and 10c. The fluid or gas entering the compressor I0 will normally have axial or Astraight flow, which is characterized by zero tangential or rotational velocity, uniform axial velocity, and uniform energy. Diagram 10a by being a single vertical line represents zero tangential velocity. Diagrams 10b and l()c by being rectangles or having uniform width from bottom to top represent uniform axial velocity and uniform energy.

The -iiuid or gas'enters the stationary blade stage I3 and the blades thereof are angled and shaped so as to cause the uid to have a rotative or tangential velocity. Since the stage is stationary, the rotating flow necessarily becomes a vortex flow, which as shown by the Diagrams 13B, 13b, and 13c involve uniform energy, uniform axial velocity, and tangential velocity inversely proportional to radius. This tangential velocity may be described as decreasingly variable when considered in an outward direction from the center of rotation. Hereafter when a velocity or energy is described as-being increasingly or decreasingly variable, it will be understood that the velocity or energy is being considered at successive points of the blade stage in question at increasingly greater distances from the center of rotation.

Since, as can be demonstrated, energy cannot be added efficiently or in large quantity to vortex flow with its decreasingly variable tangential velocity and uniform energy, it is necessary to adjust appropriately these quantities. This is accomplished by rotary blade stage I4 and stationary blade stage I5 constituting an inducer. The blades of the rotary stage I4 are so shaped and disposed as to alter the vortex flow received from the stationary stage I3 to another flow having an increasingly variable energy, as shown by Diagram 14C, which is characterized of a desired approximation of solid flow, namely, solid iiow minus vortex flow. Solid flow is flow characterized by tangential flow proportional to radius or distance from the axes of rotation. It is to be noted that the flow coming from rotary stage I4 is not solid flow, since, as shown by Diagram 14, the tangential velocity is still slightly inversely proportioned to radius, and the energy distribution has been suitably modied; the energy has been changed from uniform to increasingly variable. Some energy has been added, as is evident from a comparison of Diagrams 13c and 14, but only to the extent required for adjustment of the energy distribution as aforesaid. Itis to be noted that the axial velocity has been transformed by the rotating stage I4 to slightly increasingly variable.

The blades of stationary stage I5 are so shaped as to transform the flow coming from rotary stage I4, which was stated to have the increasingly variable energy distribution of solid flow mino; vortex flow, to solid flow minus vortex flow. This involves, as shown by the tangential velocity Diagram 15, making the tangential velocity directly proportional to radius with a correction in an amount equal to minus vortex iiow. The solid flow minus vortex iiow coming from stationary blade stage I5 is also characterized by an increasingly variable axial velocity, which has an average equal to the uniform axial velocity that would be characteristic of the aforesaid solid flow.

To summarize the function of the stages I4 and I5: these stages have converted the vortex flow resulting from the initial stationary stage I3 to solid flow minus vortex flow having increasingly variable axial velocity, which is the appropriate condition of the compressible fluid or gas for the addition of energy in significant quantity.

The compressible fluid or gas is now acted upon by the rotating blade stage I6. The blades of this stage are so shaped and disposed as to add energy in significant quantity as is to be seen from a comparison of energy Diagrams 15c and 16C. The energy distribution remains the same, or in other words the energy of the flow leaving rotary stage I6 is increasingly variable. The rotary stage I6 will necessarily have a vortex effect upon the flow and will add vortex flow to the extent of changing the flow from solid flow minus vortex flow to solid flow plus vortex flow. This can be seen from a comparison of tangential velocity Diagrams 15a and 16s. The tangential velocity in Diagram 16a is represented as less increasingly variable than that of Diagram 15e. The axial velocity hasbecome decreasingly variable as shown in Diagram 1Gb. These changes in tangential velocity and axial velocity produced as incidents of the increase in energy effected by rotary blade stage IE demonstrate the need for the flow reaching rotary stage I6 to be solid flow minus vortexv now. and to have increasingly vari.- able axial velocity.V Otherwisethe vortex flow eiect of the rotary stage I6 would cause the tangential velocity to be even lessfincreasing'y variable than shown by Diagram 16e and, per,- haps decreasingly variable4 and the axial velocity to be more decreasingly variable thanA shown by Diagram 161. Under these conditions the'addi.- tion of energywould be inefficient and s mnlllj The flow passes now tothe stationary stagel I "l, of which the blades are so shapedA and1 disposed as; to returnthe flow toapproximately its condition upon entry to rotary stage l insofar as tangential and axial velocities are concerned. The flow coming from stationary stage I1 issolid flow minus` vortex flow andv has increasingly variable tangential and axial velocities, as shown, by Diagrams 17a andA 17h. The energyI continues to be increasingly variable, as shown in Diagram 17e, for a stationary stage cannot change energy distribution..

The rotary and stationary blade4 stages I6 and il' comprise the compressor proper of the Inachine, because they cooperate to add enerii7 and to preserve the condition of the flow. Only, one Set of rotary and stationary compressor blade stages has been shown for the theoretical, considerations of Figure 1V since the action oione or several of these sets mayy if preferable be, adequately demonstrated by the description and showing of only one set for the time being; however, it is to be understood as is to be subsequently demonstrated that as many sets may be employed as may be necessary or desirable for suflcient addition of energy.

The fiovv now passes to the rotary stage I8 having blades shaped and arrangedV to alter the energy distribution of the flow to an energy diss tribution of vortex flow, to which condition the compressible, fluid or gas is later to be transformed. Vortex now has, uniform energy, and the blades of rotary stage IB` accomplish the change from increasingly variable energy of Diagram 1'7'3 to the uniform energy of Diagram 18.Y This change in energy distributionY may be made with or Without the additionA of energy. It Will be noted from velocity Diagrams 18e and 18b that the tangential and axial velocities have become less increasingly variablefthrough the action of rotary stage Il.V

The now now passes to the stationary stage I 9, having blades shaped and arranged to change the now further so that it not only has the uni-form energy distribution of vortex flow but is, vortex flow itself. The energy is uniform, asindicated by Diagram 19S; the axial velocity is uniform; and the tangential velocity is decreasingly variable.

The rotary and stationary stages I3. and t9 are to be considered an educer, since they transform the approximate solid flowresultingfrom the compressor, namely, solid now minus. vortex iiow, to Vortex flow, from which condition the change to straight or axial ilovvl by the stationary outlet blade stage 20 can be made. The change to vortex flow must be made, because otherwise the change to straight` flow cannotbe completely made. The return to straight flow is demonstrated by the Diagrams 20e, 2Gb, andZOI-, which show that it is accompanied by zero tangential or rotative velocity, and uniform energy.l A comparison of energy Diagrams 2Oc and` 10. shows the amount of energy added. to the compressible flu-id or gas by the axial-now compressor, which will be. represented. mainly bly increase in `pressure if theaxial velocity is not appreciably-changed.

yIn the more detailed physical showing oia compressor appearing; inl Figure 5. paired sets of rotor, and4 stator bladingrunning for convenience to the,v number of eight are to be noted incorporatedin the mainworking compressor portion proper 2Iv or the compressor. Compressor I0, of Winch the. embodiment shown corresponds een.- erally such es regards like reference numerals, with compressor Ill shownin Figure 1, comprises a. statorcomponent IA l and aA rotor component I2. For the mean Working compressor portion ZI, therev may be. provided en intake having Preliminary staging therein comprising an inlet grid having stator blades land an educer having respective rotor blades I4 and stator blades I 5V. As previously notedl` it isthe purpose of the grid I3 to transform the axially flowing compressor duid into. a state of vortex. flow While the induoer ele.- ments i4.' and I5 serve to.. prepare. the iluidY into an. appropriate. state for introduction into the Working compressor PQrtion of the machine l0. For the, delivery end oi the working compressor portion of which the last set of blades shownis formed. on. a stator element l, Ythere may be provided an outlet comprising final discharge or outlet means 2,0 and interpos-ed educer comprising respectively, a rotor element I8 and a stator element 19,. As set forth, hereinabove, it is the purpose of the educer to transform the fluid delivered by the working compressor portion into a state, of vortex, iQW suitable for introduction into the outlet means for restoration to straight axial' now.. Appearing directly over the axis of4 the compressor Ill oiligure 5 arel cross sections showing the blade, profiles such as may be appropriately used.V Since anyone of a Ilumber `of combinations oi blddeproles may be used to operate.accordingv to the.Y theory ofthe present invention, the form of blade actually selected is purely for purposes of illustration. For instance the angle, oi attack of the blade entrance with respect. tov the relative ovv and the angle of effective turnr or liftI may be taken from published behavior curvespfdiverse blade proiiles Well known to. the, art, for instanoa the NRA. C. A. publication. 2409.,.for Whichsee National Advisory Committee for Aeronautics Report No. 460.

In Figure, 6 is shown an enlarged view of the blade, sections just, describedV in connection with the machine of Figure 5.- Between the respective sets of blading have. been interposed fluid velocity diagrams: to serve as an aid in understanding the machine characteristic operation sought for. The blade sections selected happen. to be radially successive for convenience sake; that is to say, there appear respectively a root section, a mean intermediate section,vk and a tip section for a blade of each rotor or stator element of the machine shown. Thus inlet grid I3 of VFigure 6 corresponds with the inlet grid I3 of Figure 5. The educer rotor lil and educer stator I5` of Figure 5 correspond with the blade sections respectively shown at I4 and l5 in Figure 6. In the embodiment of Figure, `Gselected to be illustrative, the axial flow oi'j entering'fluid has 'been given an assumed velocity of 400 units. Accordingly at the root. section of inlet grid t3, at the mean intermediate section of grid I3, and at the tip section of grid [3, the straight flow vector G@ `will be observed to be directed toward the blading at zero. inclination. It is the purpose of the fixed inlet grid toA transform the straight ow such as characterizes the incoming working iiuid into vortex ilow. Hence, lthe inlet portions of the blades I3 are provided with leading .edges having a zero angle of attack to the incoming working iluid. The discharge portions of the blades I3 of the inlet grid are provided with trailing edgesof which the discharge angles vary in conformity with the flow of'fluid for providing vortex ow such as is characterized by a rotational angular velocity varying decreasingly outward. In other words, the vortex flow at the root section has a relatively higher angular rotational velocity than the mean intermediate section and at the tip section a relatively lower rotational angular velocity. Ink vector Diagram 13d the angular rotational velocity is shown to be 463 units whereas at themean intermediate section and the tip section respectively at 13e and 13f, the angular rotational velocities diminish to 377 and 323. The blade shapes and proportions may be taken as convenient from an N. A. C. A. publication in order to produce the desired result stated. Such publications also include the blade lift setting in order to bring about the proper change in direction of flow4 for a specified blade proportion. Inasmuch as the axial component and the angular rotational component of the absolute velocity of the fluid discharged from grid I3 is known, the absolute velocity of the fluid dischargedmay be determined and represented by a vector. The ilow is delivered as represented by this vector into the rotor element of an educer provided for the compressor of the instant invention, of which the rotor element is designated I4, and the stator element designated I5.

At the respective root, mean intermediate, and tip sections of rotor element I4 the blade Velocity, varying outward. with radius, is represented as of the order respectively of 700 units, 864 units, and 1003 units in Figure 6. The addition of this blade velocity vectorwise to the vector representing the flow of iiuid from inlet grid I3 will yield a resultant vector shown in Figure 13d at |02, in Figure 13e at |04, and in Figure 13f at |08. These resulting vectors are representative of the relative iiow of fluid incoming to inducer rotor element I4. It will be seen .that` the inlet portions of the blade sections of rotor I4 are provided with leading edges presenting a substantially zero angle of attack to the respective velocities represented by vectors |02, I04, and 106. The radially successive sections of the rotor blade I4` may be noted to have an angle of lift increasing outwardly. That is to say, the zero lift line I03 of the basic section adjacent the rotor element in Diagram 13d at the` root of the blade lies substantially parallel with the uid ilow discharge lines. The difference between the inlet and discharge angle at the root section of blade I4 will be seen to comprise an angle X14 of minor consequence. The difference between thev inlet and discharge anglesvof fluid for the mean intermediate section of blade I4 isof the relatively larger quantity Y1'. in Diagram 14e, and the difference between the entrance to discharge velocities at the tip section Diagram 14f of blade I4 amounts to a still larger angle Zu. Vectorially computable from the .relative discharge velocity from blade I4 and the blade velocity, is the absolute discharge velocity of the fluid leaving blade I4 shown to be of the value of 585 in Diagram 14d, 620 in Diagram 14, and660 in Diagram 14f. These increasingly variable absolute velocities just noted yield a tangential component which will conform substantially to a mean value at all radii, namely, the angular rotational velocity 478 at the root in Diagram 14d, 472 at the intermediate section according to Diagram 14e, and 467 at the tip section in accordance with Diagram 14f.

The inducer stator blading in Figure 6 next in succession comprises a blade I5 of which the inlet portion presents a leading edge having a substantially zero angle of attack to the oncoming fluid. The basic tip section of blade I5 will be seen to have a zero lift line |01 lying in Diagram 15t in substantial parallelism with the normal or natural flow of uid introduced into the inducer stator element, thus making for a relatively inconsequential change in direction denoted -by angle Zia of Figure 15t of the inlet to discharge velocities. The change of inlet and discharge velocities, or as ordinarily stated, the angle of lift of blade I5 is of a greater order of value Yis at the mean intermediate section, as shown ,in Figure 15e and at the root section of angle of lift attains a value of X15, which is even greater as shown at Figure 15d than the angle of lift at Figure 15e. Blade I5 hence has an angle of lift varying inversely with radius as is contrasted with blade I4 which angle of lift varies with radius.

This decreasing characteristic of variation in inlet and discharge angle with respect to radius in blade I5 has a decided eiect on the discharge velocities from the discharge portions of blade I 5. The discharge velocities shown in Diagrams 15d, 15. and 15f to be of the value 418, 510, and 595 vary increasingly outward and with appropriate clockwise change in direction such that the absolute angular rotational velocity of the radially successive sections outward have the increasingly variable characteristic substantially of solid iiow. The absolute angular rotational velocity in Diagram 15d will be seen to be 215, while at the mean intermediate section shown by Diagram 15e the absolute angular rotational velocity is of the value 315, and at the tip section as diagrammed at 15f the absolute angular rotational velocity is of value 398. In this flow condition of modified solid iiow the motive fluid may suitably be introduced into the working compressor means.

The first element of the working compressor means of Figure 6 is shown to be a rotor I6 of which the root section has a blade speed of 700, the mean intermediate section has a blade speed of 852, and the tip section has a blade speed of 987. A vectorial addition as in Diagrams 15d, 15, and 15t of the absolute fluid discharge velocity and the absolute blade velocity will yield a vector as at |08, IIO, and II2, which illustrates the relative ow of incoming fluid as respects the working compressor rotor I6. In the state of flow in which the iluid is delivered to the Working compressor means, energy may be added in relatively great amounts for each successive stage of the compressor traversed at a relatively high degree of eiciency. The working compressor serves to increase the pressure on the iiuid passing therethrough and at the same time preserves that characteristic in flow received from the inducer means of outwardly increasing angular rotational velocity and absolute velocity, that is. the velocities 418 and 215 of Diagram 15d, 510 and 315 of Diagram 15e, and 595 and 398 of Diagram 15t or approximations of those values. It has been found that upon reception of a iiuid in the state at which the inducer delivered it, the working compressor means can operate to full advantage if it is designed to operate along the lines of symmetrical iiow diagram principles. For one thing, the pressure rise in each stator or rotor element is the same according to a symmetrical flow diagram regardless of whether in stator or rotor. The change in direction of llow of the uid passing through each set of blades is also of the same size angularity even if of opposite algebraic sign as compares the stator and rotor element. By way of amplifying on the subject of symmetrical flow diagrams,l it might be said that the symmetrical ilow desirably takes place at the mean intermediate `section of the blade with properaccommodations being provided for at the tip and root sections by readily done compensations in the appropriate velocity diagrams. The mean intermediate section of blade l will be seen to yieldsuch a velocity diagram as at 16e. The angle of lift 'X16 in T16e serves as a measure of the changeofangularity of the fluid in passing through themean intermediate section of blade I6. y

In Figure 7 the velocity vector Diagram `16 of Figure 6 has been'reproduced in part and 4thereover in Figure 7 'has been superimposed the 'entrance velocity E.VRe1, relative to the Smean intermediate section of blade I6 'as shownin velocity Diagram e. The change of entrance to discharge angle measured by anglev Y1@ of Diagram I6@ likewise appears in Figure 1'7. The change of vectors wrought by the angle change Yie is represented by the Vvalue Acunei. Additionally superimposed in Figure 7 is the absolute discharge velocity DVM. from the working compressor first stator element l1. In the velocity Diagram 17e of the mean intermediate section of blade I1, appears "the change .of entrance to discharge angle Yu 'which will also be found among the superimposed diagrams of Figure 7. The vector change wrought by this change o'f angle will be seen in Figure 7 'to amount "to the vector diierence AcuAts. Ina'sniuch as 'the vaxial component of the uid ow in the working compressor blading I6 and l1 i's substantially constant through the mean intermediate section, the resulting right triangles are in essentials symmetrical with respect to 'the 'axis ofthe machine. The change in relative flow of fluid to and from the rotor element I6 is substantially the 'same as the change of absolute velocity respecting direction of flow to 'and from `the stator element i1. Inasmuch as the quantity s along the base of the resulting triangle approximates the quantity t along the base of the triangle, a diagram results in' Figure 7 which is substantially symmetrical about the axial velocity now component 489 and axis of the machine. As stated, since the change in direction of Vthe angles of llow of the iiuid in going through each set of working compressor blading, regardless of the identity of the blading being rotor or stator, is substantially the same, a pressure rise maybe achieved between each 'successive st o'f blading which is also substantially the same. By Way of return to Figure 6 it is to be noted in the vector Diagrams 17d- -17e and 171 that the absolute velocities are still preserved in Yproportion so 'as to vary increasingly outward and to have an angular rotational component likewise varying increasingly outward from vthe value v215 in Diagram 17d to the value 380 in Diagram 171.

In Figure 8 appears an assemblage of the blade sections and vector diagrams which correspond to another section of the machine of Figure 5. The vector Diagrams 17d, 17e, and 17I have been reproduced as carriedover from Figure 6 and serve to illustrate the characteristic of ow of the fluid discharged from stator e`lez`nent"l1 of gram 26a may be lsuperimposed the relative entrance velocity EVRei of Figure 17e and .the discharged absolute 'velocity DVAbs of Figure 27e of the respective 4mean. intermediate blade sections of blades 26 andl21. 'The resulting diagram will 'be substantially symmetrical with respect to the axis of the machine, .as is indicative of the eventuality o'f equal pressure rise transpiring in blading 26 and in 'blading 21. Subsequent to these two successive pressure rises, the working .iuid will be discharged from the trailing edge of the discharge portion of blade 21 inthe fashion of velocity Diagrams 27d, 27e, and 27f. It will be noted that the absolute velocities in Diagrams 1 27d, 2:79, and-T27`fvar-y from the evalues420 to 550 while the angular rotational velocities vary from 215 outward `to 364,'bothsets of velocities having an increasing .outward characteristic. In Figure `8Vt`he velocity diagrams, intermediate Diagrams .27d, 27, and 27f and the Diagrams 87d, 87e, and 87f have been omitted, being largely a reproduction of the diagrams given `for blades I6, l1, 26, and 21. Actually, Vas many working compressor .stages may `be provided as is appropriate for thel pressure rise `desirable and for, the purposes of Figure k5 some eight sets of rotorrand stator blading have been shown. The last row in the` working compressor portion of the machine in Figure `5 comprises blades B1, the sections of which appear also in -Figure 8. -As is a factbrought out rby the diagrams for velocity 87d, 87e, and 87f of Figure f8, the increasing outward characteristic of absolute velocity and angular yrotational velocity isstill maintained in the fluid flow upon discharge from the working'compresser Vstator blade 81. At the root thereof the absolute velocity will vbe seen to `be 445, at the mean intermediate section 465, and as accords with velocity Diagram 87f, 495 at the tip. The respective angular rotational velocities of the radially successive blade sections of velocity'Diagrams 871, 87e, and 87f are respectively 215, 243, and 271.

In Figure 8 'the lilzevreerence ynumerals it, i9, and .2G correspond vwith the reference numerals yof the blading of Figure 5. Between the outlet means 2B inFigure 8.'.and4the last set of blading -81 ,in theworking compressor yis interposed the educer comprising rotor element i8 and stator element |49. The tip section of lthe rotor blade IB will be observed to haveHa-speed-of 780, whereas the `mean intermediate section has a blade speed of 74i0,.and the root section a blade speed of 700. yWhen these quantities are added vecytorially to the increasing absolute velocities noted in the respective velocity Diagramsf87 87e, and 87d, the vresulting relative .incoming velocity assumes the values `varying increasingly outward at 615 in Figure 87d, V64.0.i'n Figurei7e, and 655 in Figure'87f. 'The trailing edgesof the educer rotor IB are proportioned and set for a fluid turning therethrough such as to bring into substantial uniformity the relative discharge velocities, These angles of lift or angles of turn indicated respectively atX1a,Y1c, and Zia yield respectively laeoaerse the relative discharge velocities of value 475 in Diagram 18d, 478 in Diagram 18e and 482 in Diagram 181, a substantially. constant value. VvMoreover, from an examination .of Figures 87d, 87e, and 871 in comparison with the respective Figures 18d, 18e, and 181, it will be revealed that the absolute angular rotational velocities have been in effect increased by blading I8 inversely with radius such that they likewise approach being substantially constant. That is to say, the tangential velocity 215 of Diagram 87d has been increased during passage through blading i8 by a relatively large amount to yield the value 485 in Diagram 18d; theangular rotationalv velocity 271 of Figure 871 has been changed during passage of the fluid through the tip section of blade I8 by a relatively lesser amount to result in an angular rotational velocity of 475 in Diagram 181, which is substantially the same as the angular rotational velocity 485 of Diagram 18d. Similarly the angular rotational velocity at the intermediate section of the blade will be noted to have been changed to 480 in Diagram 18e. vIn the stator blading I9 of the educer, the inlet and discharge portions have been so proportioned and set as to provide an angle of lift causing a decrease, in variance with radius outwardly, of absolute angular rotational velocity. The angular rotational velocity will be observed to have changed at the root section from 485 in Diagram 18d to 256 in Diagram 19d; from 480 in Diagram 18e to 243 in Diagram 19e, and from 475 in Diagram 181 to 230 as accords with velocity Diagram 191. These changes, owing to the angle of lift of the stator blades, are such as to yield an angular rotational velocity along the trailing edge of blade I9 varying inversely with radius, decreasing from the root outwardly from 256 to 243 and thence to 230. The absolute velocities will be noted in the transition from Diagrams 18d, 18e, and 181 to Diagrams 19d, 19e, and 191 to have been slowed relatively proportionately, that is from 640 to 435, from 625 to 425 at the mean intermediate section, and from 605 to 415 at the tip and yet with theensuing turn-angle in blade I9 providing a residual spin component to flow such that the tangential or-angular rotational velocity decreases from the element outward as characterizes vortex ilow. Once has this vortex flow been re-established as accords with velocity Diagrams 19d, 19e, and 191, the compressible fiuid in the compressor-will be understood to have completed the stages of transition following its passage from the original inlet grid.

The blades 20 in Figure 8, which comprise the outlet means, serve in a reverse function to that of the blades of the initial inlet means. The discharge portions of the stator outlet 20 are formed with trailing edges which conform to and effect a fluid discharge substantially free from rotation. The inlet portions of blade 20 are formed so as to present a leading edge of substantially zero angle of attack to the oncoming compressible fluid discharged from the educer and the lift angle selected for the blade then is that angle necessary to remove the residual rotation or spin from the compressible fluid and establish once again an axial flow in a state of equilibrium. It is to be appreciated of course, that during the progress through the compressor the compressible gas has undergone such pressure rise as may be desirable and commensurate with the number of stages for which the compressor is designed. Both the inducer and educer have been shown each as comprising only a single 'set of rotary and stationary blades, but it is to be understood 12 Ithat each may comprise more thanone set if desired. y

The foregoing machine has b een described as a compressor but it may also be a turbine within the spirit of the present invention. Compressible fluid or gas with relatively high energy content is so carried as to flow through the machine transferring energy to the machine by causing the rotor to rotate in this latter regard. The changes in the flow through the machine acting as a turbine will be similar to vthose described for flow through the machine acting as a compressor except that energy of the motive fluidat the end will be less rather than more than at the start and energy will be abstracted rather than added while the energy is variable along the lengths of the blades of the stages.

The invention has been described byv means of preferred embodiment illustration but it is not intended to limit the presentinvention from the inclusion of other equivalent variations and changes in construction such as will be apparent to those skilled in the art.

What isV claimed is:

1. A'rotary axial-flow fluid power conversion machine having a longitudinal axis, and comprising: a stator elementhaving blades provided with inlet and discharge portions, the inlet portions of the blades being parallel with the axis of the machine and the surfaces of the blades being so curved that the discharge portions thereof are disposed to the axis of the machine at an angle such that the angular rotational velocity of the motive fuid discharged therefrom varies inverselywith the distance of the discharge portion surfaces from the axis of the machine; inducer means in series with the stator element and including rotor and stator elements having blades provided with curved surfaces and having inlet and discharge portions, the blades being so curved that discharge portions of the inducer rotor blades are proportioned and set to produce a variation in the inlet and discharge angles of the motive fluid with respect to relative distance of the discharge portion surfaces from the axis of the machine such that the absolute angular rotational velocity of all said fluid discharged from the inducer rotor blade discharge portions is in substantial equality therealong, the discharge portions of the inducer stator blades being proportioned and set to produce a variation in the inlet and dischargeV angles with respect to the distance of the discharge portion surfaces to the axis of the machine such that the absolute angular rotational velocity of the discharged fluid varies with the distance of thedischarge portion surfaces of the inducer stator blades from the axis of the machine, working compressor` means in series with the inducer meansincluding rotor and stator elements having blades provided with curved surfaces and having inlet and discharge portions, the last element in the series of working compressor elementsl being a stator element having the surfaces of the blades thereof rso curved that the discharge portions of theblades are disposed to the axis of the machine at an angle such that the relative and angular rotational velocities of the discharged fluid vary with the distance of the discharge portion surfaces from the axis of the machine; educer means in series with the Working compressor means and including rotorA and stator elements having blades with curved surfaces and being provided with inlet and discharge portions, the discharge portions of the rotor blades being proportioned and set for turning and slowing the final discharge from the working compressor means to bring the 'absolute angular rotational velocity of all said fluid discharged from the rotor blades into substantial equality therealong, with the surfaces of the educer vstator blades being so curved that the discharge .portions thereof are disposed at an angle to the axis of the machine such that the absolute angular rotational velocity of the motive nuid discharged'. therefrom varies inversely with the distance of the discharge lportion surfaces from the axis of the machine; and outlet means in series with the 'educer lmeans land including a stator element having vblades with curved surfaces and being 4providedvvith inlet and discharge portions, the blades 'of the stator ele-- ment being so curved that vthe 'discharge portions thereof are disposed parallel to 'the laxis of the machine such as to conform tofnd effect all-uid discharge substantially ff-'ree from rotation.

2. A rotary axial-flow uid 'power conversion machine having a longitudinal axis, and comprise ing: a stator element having blades lprovided with inlet and discharge portions, the inlet Vportions of the blades being parallel fwithth'e 'axis of the machine and the surfaces of the blades being so y'curved that the 'discharge portions thereof are 'disposed to the axis of the machine at an `angle such that the angular'frotational velocity of the motive fluid discharged therefrom varies inversely with the distance of the discharge portion surlfaces from the axisof the machine; inducer means in series with the statorrelement and includingrotor and stator lelements having blades provided with curved surfaces and having inlet and discharge portions, the blades being so curved that discharge portions of the induoer'rotor blades 'are proportioned and set to produce a variation in the inlet' vand discharge angles of the motive fluid with respect to relative distance of the discharge portion 'surfaces from the axi'sof the machine Vsuch that the absolute angular rotational velocity of all said fluid discharged from the inducer rotor blade discharge portions is in substantial equality therealong, the discharge portions of the inducer stator blades being proportioned and set to produce a variation in the inletl and discharge angles with respect to the distance of the discharge portion surfaces to the axis of the machine such that the absolute angular rotational velocity of the discharged fluid varies with the distance of the discharge portion surfaces of the inducer stator blades from the axis of the machine, working compressor means in series with the inducer means including rotor and stator elements having blades provided with curved surfaces and having inlet and discharge portions, the rotor and stator elements being operatively arranged respectively in series with the inducer means and the discharge portions of the respective blades thereof being proportioned and set for a variation in the inlet and discharge angles at the mean distance of the discharge portion surfaces from the axis of the machine such that the change of inlet to discharge uid velocities relative to working compressor rotor element in respect of the axis of the machine is substantiallyV the equivalent of and opposite to the change of inlet to discharge fluid velocities relative to the succeeding working compressor stator element in respect of the axis of the machine, the last element in the series of working compressor elements being a stator element having the surfaces of the blades thereof so curved that the discharge portions of the blades are disposed to the axis of the machine at an angle such that the relative and 14 angular 'rotational velocities of 'the' discharged fluid vary with the di'stance'of the discharge portion surfaces from 'the axis of. the machine; educ'er means in series withthe working compressor means and includingrotor and stator elements having blades with curvedsurfa'ces and being provided with inlet and 'discharge portions, the discharge portions of the rotor blades being proportioned and set for turning and slowing the final discharge from the working compressor means to bring the absolute angular rotational velocity rof all said fluid discharged from the rotor blades into substantial equality therealong, with the surfaces of the educar stator blades being so curved that the discharge portions thereof are disposed at an angle to the `axisrof the machine such that the absolute fangularrotational 4velocity of the motive huid discharged therefrom varies inversely with the distance of the discharge portion surfaces from the laxis of the machine; and Vout-let means in series withthe educer means `and-including a stator element having 'blades with curved surfaces and being provided with inlet yand discharge portions, the blades ofthe lstator element beingk so curved that the discharge portions thereof are vdisposed parallel to the axis of the machinesuch as to conform 'to ande'ifect a fluid dis'clfiarge''sub stantially free 'from rotation. l

3. In Van axial flow rcompressor 'characterized by a working compressor portion comprising 'sets of xed blades, land-rotor andstat'or parts in,v

series with 'one another including 'la discharging stator part rwhich constitutes th'e last said part in series and *which carries fone set of the fixed blades aforesaid, said onesetfof fixed blades 'being provided curvedisurfacesand- 4having inlet and'- discharge portions, 'said discharging stator partfhavingfsaid one vset of fixed blades 'so curved that the discharge portions of 'the Vblades are disposed to the ax'isjof the compressor Ja't an angle suchv that the relative and angular discharge rotational velocities 'ofA the fluid dis-A charged from'the discharge 'portions of the dis;- charging statorpart vary with "the distance 'of the discharge portion surfacesv from the axis of the machine: -educing andnal 'discharge means in series with the working compressor Vmeans and including blades with curved 'surfaces provided with inlet and discharge portions; and 4a plurality of elements carrying the blades vii'x'ed 'thereto, one of said elements constituting a'rotor arranged adjacent vsaid discharging stator part withv the discharge vportions of the rotor -blades proportioned and set -with respect to the axis of the compressor for turning and slowing the nnal discharge from the working compressor means to bring the absolute angular rotational velocity of all said fluid discharge from the rotor blades into substantial equality along the discharge portions of the latter, the remainder of said elements comprising a stator unit in series with the rotor aforesaid and having the blades thereof selected and set for slowing and turning the flow of the fluid in effectively removing the residual rotation from the nal discharge and establishing axial flow in state of equilibrium, the final discharge portions of the sets of fixed blades, and rotor'and stator parts in series with one another including a discharging stator part which constitutes the last said part in series and which'carries one set of the fixed blades aforesaid,'said one set of fixed blades being provided with curved surfaces and having inlet', and discharge portions, said discharging stator part having saidV one set of xed blades so curved that the discharge portions of the blades are disposed to the axis of the compressor at an angle such that the relative and angular discharge rotational velocities of the fluid discharge from the discharge portions of the discharging stator part vary with the distance of the discharge portion surfaces from the axis of the machine: educer'means in series with the working compressor means and including rotor and stator elements having blades with curved surfaces and being provided Vwith inlet and discharge portions, the discharge portions of the rotor blades being proportioned and set for turning and slowing the nal discharge from the working compressor means to bring the absolute angular rotational lvelocity of all said fluid discharged from the rotor blades into substantial equality therealong, with the surfaces of the educer stator blades vbeing so curved that the discharge portions thereof are disposed at an angle to the axis of the compressor such that the absolute angular rotational velocity of the motive uid discharged therefrom varies inversely with the distance of the discharge portion surfaces from the axis of the compressor; and outlet means in series with the `educer means and including a stator element havingblades with curved surfaces and being provided with inlet and, discharge portions, the blades of the stator element being so curved that the discharge portions thereof are disposed parallel to the `axis ofthe compressor such as to conform to and effect a fluid discharge substantially free from rotation.

5. A rotary axial-flow compressor having a longitudinal axis, and comprising: astator element having blades provided with inlet and discharge portions,A the inlet portions of the blades being parallel with theaxis of the compressor and the surfaces of the blades being so curved that the discharge portionsvthereof are disposed to the axis of the machine at an angle such that the angular rotational velocity of the motive fluid discharged therefrom varies inversely with the distance of the discharge portion surfaces from the axis of the compressor; inducer means in series with the stator element and including rotor and stator elements having blades provided with curved surfaces and having inlet and discharge portions, the blades being so curved that discharge portions of the inducer rotor blades are proportioned and set to produce a variation in the inlet and discharge angles of the motive fiuid with respect to relative distance of the discharge portion surfaces from the axis of the compressor such that the absolute angular rotational velocity of all said fluid discharged from the inducer rotor blade discharge portions is in substantial equality therealong, the discharge portions of the inducer stator blades being proportioned and set to produce a variation in the inlet and discharge angles with respect to the distance of the discharge portion surfaces to the axis of the compressor such that the absolute angular rotational velocity of the discharged fluid varies with the distance of the discharge portion surfaces of the inducer stator blades from the axis of the compressor; and working compressor means in series with the inducer means including rotor and stator elements having blades provided with curved surfaces and having inlet and discharge portions, the rotor and stator elements being operatively arranged respectively lin series with the inducer means and the discharge portions of the respective blades thereof being proportioned and set for a variation in theinlet and discharge angles at the mean distance of the discharge portion surfaces from the axis of the compressor such that the change of inlet to discharge uid velocities relative Vto working compressor rotor element in respect of the axis of the compressor is substantially the equivalent of and opposite to the change of inlet to discharge fluid velocities relative tothe succeeding working compressor stator element in respect of the axis of the machine, the last element in the series of working compressor elements being a stator element having the surfaces of the blades thereof so curved that the discharge portions of the blades are disposed to the axis `of the compressor at an angle such that the relative and angular rotational velocities of the discharged fluid vary with the distance of the discharge portion surfaces from the axis vof the compressor.

f FRANK J. GARDINER.

yfile of this patent:

UNITED STATES PATENTS l Number Name Date 2,378,372 Whittle June 12, 1945 2,334,000 j Wattendorf Sept. 4, 1945 

